GB757471A - Improvements in or relating to axial flow compressors - Google Patents

Abstract

757,471. Axial-flow compressors; jetpropulsion engines. SZYDLOWSKI, J. Oct. 22, 1954 [Oct. 23, 1953; Aug. 5, 1954], No. 30528/54. Classes 110(1) and 110(3) In an axial-flow impeller for a compressor, particularly a compressor forming part of an aircraft jet-propulsion or gas turbine engine and operating at transonic and supersonic speeds, the camber line of the blades is curved in opposite directions at the tip and at the root end. Fig. 3 shows the cross-section of the compressor blades 3 at their root ends, the centre of curvature of the camber line of each blade being located with respect to the blade in the direction F of impeller rotation. At the mid-length of the blade, the curvature is in the same direction, but the radius of curvature is greater. Further towards the blade tip, the camber line is straight, while at the tip the curvature is in the opposite direction to that at the root end. In a modification, the curvature at mid-length is already opposite to that' at the root end. In the jet-propulsion engine shown in Fig. 6, the impeller of the low-pressure compressor 11 is constructed as described above, and supplies air both to a highpressure compressor 13 and to a by-pass duct 12. Compressor 13 supplies air to the combustion chamber 14 of a gas turbine 15. Specification 693,227 is referred to.